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S4310 (s4310-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 50,000
Max Cl/Cd: 36.32 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4310-il-50000-n5.txt
Download as CSV file: xf-s4310-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2898   0.10800   0.10146  -0.0378   1.0000   0.1121
  -8.750  -0.3032   0.10681   0.10044  -0.0398   1.0000   0.1139
  -8.500  -0.3176   0.10554   0.09937  -0.0404   1.0000   0.1143
  -8.250  -0.2957   0.10039   0.09422  -0.0375   1.0000   0.1177
  -8.000  -0.3005   0.09837   0.09231  -0.0360   1.0000   0.1188
  -7.500  -0.2586   0.08292   0.07743  -0.0385   0.9858   0.0653
  -7.000  -0.3565   0.08502   0.07930  -0.0417   0.9888   0.0582
  -6.750  -0.3375   0.08061   0.07484  -0.0449   0.9809   0.0564
  -6.500  -0.3188   0.07539   0.06957  -0.0510   0.9715   0.0544
  -6.250  -0.3018   0.06981   0.06388  -0.0575   0.9611   0.0524
  -6.000  -0.2837   0.06354   0.05740  -0.0645   0.9511   0.0504
  -5.750  -0.2605   0.05599   0.04937  -0.0725   0.9427   0.0482
  -5.500  -0.2419   0.05139   0.04438  -0.0755   0.9327   0.0481
  -5.250  -0.2153   0.04849   0.04129  -0.0781   0.9259   0.0503
  -5.000  -0.1910   0.04518   0.03758  -0.0803   0.9176   0.0525
  -4.750  -0.1625   0.04154   0.03339  -0.0826   0.9108   0.0537
  -4.500  -0.1352   0.03842   0.02970  -0.0838   0.9031   0.0544
  -4.250  -0.1034   0.03566   0.02629  -0.0852   0.8971   0.0563
  -4.000  -0.0766   0.03370   0.02380  -0.0854   0.8891   0.0599
  -3.750  -0.0418   0.03195   0.02182  -0.0869   0.8842   0.0640
  -3.500  -0.0182   0.03069   0.02027  -0.0860   0.8753   0.0669
  -3.250   0.0169   0.02931   0.01854  -0.0869   0.8702   0.0731
  -3.000   0.0401   0.02854   0.01770  -0.0862   0.8614   0.0806
  -2.750   0.0742   0.02747   0.01644  -0.0868   0.8560   0.0896
  -2.500   0.0985   0.02684   0.01574  -0.0862   0.8476   0.1046
  -2.250   0.1306   0.02588   0.01489  -0.0869   0.8417   0.1448
  -2.000   0.1537   0.02494   0.01453  -0.0866   0.8334   0.2523
  -1.750   0.1771   0.02364   0.01435  -0.0858   0.8272   0.4898
  -1.500   0.2395   0.02220   0.01389  -0.0894   0.8247   1.0000
  -1.250   0.2592   0.02250   0.01380  -0.0882   0.8147   1.0000
  -1.000   0.2858   0.02269   0.01362  -0.0880   0.8072   1.0000
  -0.750   0.3106   0.02292   0.01354  -0.0876   0.7989   1.0000
  -0.500   0.3345   0.02319   0.01354  -0.0870   0.7905   1.0000
  -0.250   0.3621   0.02336   0.01345  -0.0868   0.7832   1.0000
   0.000   0.3842   0.02370   0.01358  -0.0859   0.7740   1.0000
   0.250   0.4139   0.02381   0.01348  -0.0860   0.7675   1.0000
   0.500   0.4345   0.02421   0.01372  -0.0849   0.7577   1.0000
   0.750   0.4660   0.02425   0.01358  -0.0851   0.7518   1.0000
   1.000   0.4854   0.02471   0.01392  -0.0840   0.7413   1.0000
   1.250   0.5115   0.02493   0.01401  -0.0835   0.7334   1.0000
   1.500   0.5371   0.02517   0.01414  -0.0830   0.7249   1.0000
   1.750   0.5595   0.02554   0.01443  -0.0821   0.7153   1.0000
   2.000   0.5896   0.02556   0.01436  -0.0820   0.7085   1.0000
   2.250   0.6100   0.02601   0.01476  -0.0809   0.6977   1.0000
   2.500   0.6359   0.02621   0.01491  -0.0804   0.6891   1.0000
   2.750   0.6626   0.02635   0.01501  -0.0798   0.6803   1.0000
   3.000   0.6841   0.02674   0.01538  -0.0788   0.6695   1.0000
   3.250   0.7118   0.02681   0.01542  -0.0783   0.6611   1.0000
   3.500   0.7369   0.02700   0.01560  -0.0776   0.6512   1.0000
   3.750   0.7584   0.02737   0.01601  -0.0766   0.6399   1.0000
   4.000   0.7838   0.02753   0.01617  -0.0758   0.6299   1.0000
   4.250   0.8124   0.02749   0.01613  -0.0753   0.6208   1.0000
   4.500   0.8333   0.02787   0.01656  -0.0742   0.6086   1.0000
   4.750   0.8557   0.02816   0.01692  -0.0732   0.5968   1.0000
   5.000   0.8804   0.02831   0.01712  -0.0723   0.5856   1.0000
   5.250   0.9090   0.02820   0.01703  -0.0717   0.5753   1.0000
   5.500   0.9318   0.02843   0.01732  -0.0707   0.5626   1.0000
   5.750   0.9534   0.02871   0.01771  -0.0695   0.5492   1.0000
   6.000   0.9754   0.02896   0.01803  -0.0684   0.5356   1.0000
   6.250   0.9974   0.02920   0.01834  -0.0672   0.5216   1.0000
   6.500   1.0195   0.02944   0.01865  -0.0660   0.5074   1.0000
   6.750   1.0413   0.02968   0.01899  -0.0648   0.4927   1.0000
   7.000   1.0629   0.02995   0.01933  -0.0636   0.4776   1.0000
   7.250   1.0841   0.03024   0.01968  -0.0623   0.4622   1.0000
   7.500   1.1051   0.03056   0.02005  -0.0611   0.4465   1.0000
   7.750   1.1248   0.03097   0.02053  -0.0597   0.4304   1.0000
   8.000   1.1410   0.03161   0.02126  -0.0581   0.4136   1.0000
   8.250   1.1570   0.03227   0.02199  -0.0565   0.3969   1.0000
   8.500   1.1727   0.03297   0.02274  -0.0548   0.3804   1.0000
   8.750   1.1878   0.03371   0.02354  -0.0532   0.3642   1.0000
   9.000   1.2019   0.03452   0.02443  -0.0514   0.3484   1.0000
   9.250   1.2141   0.03542   0.02536  -0.0495   0.3332   1.0000
   9.500   1.2252   0.03641   0.02641  -0.0476   0.3184   1.0000
   9.750   1.2352   0.03752   0.02757  -0.0457   0.3040   1.0000
  10.000   1.2446   0.03875   0.02886  -0.0440   0.2903   1.0000
  10.250   1.2529   0.04008   0.03026  -0.0422   0.2769   1.0000
  10.500   1.2607   0.04151   0.03181  -0.0406   0.2642   1.0000
  10.750   1.2686   0.04300   0.03339  -0.0390   0.2521   1.0000
  11.000   1.2763   0.04453   0.03497  -0.0376   0.2404   1.0000
  11.250   1.2855   0.04599   0.03647  -0.0363   0.2293   1.0000
  11.500   1.2874   0.04813   0.03880  -0.0349   0.2187   1.0000
  11.750   1.2912   0.05018   0.04098  -0.0337   0.2088   1.0000
  12.000   1.2980   0.05198   0.04283  -0.0327   0.1992   1.0000
  12.250   1.2998   0.05434   0.04541  -0.0317   0.1902   1.0000
  12.500   1.3013   0.05683   0.04806  -0.0309   0.1819   1.0000
  12.750   1.3097   0.05855   0.04975  -0.0300   0.1734   1.0000
  13.000   1.3020   0.06220   0.05373  -0.0297   0.1663   1.0000
  13.250   1.3098   0.06412   0.05567  -0.0290   0.1589   1.0000
  13.500   1.2990   0.06836   0.06021  -0.0291   0.1527   1.0000
  13.750   1.3066   0.07027   0.06211  -0.0286   0.1456   1.0000
  14.000   1.2899   0.07558   0.06776  -0.0295   0.1408   1.0000
  14.250   1.2892   0.07877   0.07106  -0.0296   0.1350   1.0000
  14.500   1.2805   0.08327   0.07574  -0.0305   0.1303   1.0000
  14.750   1.2579   0.09017   0.08292  -0.0328   0.1267   1.0000
  15.000   1.2741   0.09065   0.08331  -0.0319   0.1196   1.0000
  15.250   1.2414   0.09985   0.09284  -0.0359   0.1178   1.0000
  15.500   1.1982   0.11207   0.10530  -0.0421   0.1168   1.0000
  15.750   1.1158   0.13553   0.12875  -0.0556   0.1168   1.0000
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